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  • 1
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    A transonic rectangular grid embedded panel method (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: In this chapter, a description is given of a nonstandard method which has the ultimate goal to provide a routine solution of transonic flow problems about large, complex configurations. For a number of reasons, it is difficult to extend standard methods to the solution of flows about complicated configurations. According to the particular approach of the considered nonstandard method, in the process of solving for linear potential flow via panel methods, a flow everwhere in space is created, taking into account the interior of the aircraft as well as the external flowfield of interest. Attention is given to the solution of flow problems without interior boundaries, the treatment of interior boundaries, and areas of current and future research.
    Keywords: AERODYNAMICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    TranAir: A full-potential, solution-adaptive, rectangular grid code for predicting subsonic, transonic, and supersonic flows about arbitrary configurations. User's manual (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The TranAir computer program calculates transonic flow about arbitrary configurations at subsonic, transonic, and supersonic freestream Mach numbers. TranAir solves the nonlinear full potential equations subject to a variety of boundary conditions modeling wakes, inlets, exhausts, porous walls, and impermeable surfaces. Regions with different total temperature and pressure can be represented. The user's manual describes how to run the TranAir program and its graphical support programs.
    Keywords: AERODYNAMICS
    Type: NASA-CR-4349 , A-90092 , NAS 1.26:4349
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    TRANAIR - A computer code for transonic analyses of arbitrary configurations (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Attention is given to a new approach to solving full potential equations about arbitrary configurations. Numerical algorithms from such fields as finite elements, preconditioned Krylov subspace methods, discrete Fourier analysis, and integral equations are combined to take advantage of the size and speed of current and emerging supercomputers. On the basis of this appraoch, a robust, efficient and easy to use computer code referred to as TRANAIR has been developed for transonic analysis of complex geometries.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-0034
    Format: text
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  • 4
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    Development and flight tests of vortex-attenuating splines (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The ground tests and full-scale flight tests conducted during development of the vortex-attenuating spline are described. The flight tests were conducted using a vortex generating aircraft with and without splines; a second aircraft was used to probe the vortices generated in both cases. The results showed that splines significantly reduced the vortex effects, but resulted in some noise and climb performance penalties on the generating aircraft.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8083 , L-10442
    Format: application/pdf
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  • 5
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    Preliminary results of flight tests of vortex attenuating splines (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flight tests have been conducted to evaluate the effectiveness of a wingtip vortex attenuating device, referred to as a spline. Vortex penetrations were made with a PA-28 behind a C-54 aircraft with and without wingtip splines attached and the resultant rolling acceleration was measured and related to the roll acceleration capability of the PA-28. Tests were conducted over a range of separation distances from about 5 nautical miles (n. mi.) to less than 1 n. mi. Preliminary results indicate that, with the splines installed, there was a significant reduction in the vortex induced roll acceleration experienced by the PA-28 probe aircraft, and the distance at which the PA-28 roll control became ineffective was reduced from 2.5 n. mi. to 0.6 n. mi., or less. There was a slight increase in approach noise (approximately 4 db) with the splines installed due primarily to the higher engine power used during approach. Although splines significantly reduced the C-54 rate of climb, the rates available with four engines were acceptable for this test program. Splines did not introduce any noticeable change in the handling qualities of the C-54.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-71928
    Format: application/pdf
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  • 6
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    A transonic rectangular grid embedded panel method (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A method is presented that has the potential for solving transonic flow problems about the same complex aircraft configurations currently being analyzed by subsonic panel methods. This method does not require the generation of surface fitted grids. Instead it uses rectangular grids and subgrids together with embedded surface panels on which boundary conditions are imposed. Both the Euler and full potential equations are considered. The method of least squares is used to reduce the solution of these equations to the solution of a sequence of Poisson problems. The Poisson problems are solved using fast Fourier transforms and panel influence coefficient techniques. The overall method is still in its infancy but some two dimensional results are shown illustrating various key features.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 82-0953 , Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference; Jun 07, 1982 - Jun 11, 1982; St. Louis, MO
    Format: text
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    NASA TECHNICAL REPORTS
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